EP0899438A1 - Gas turbine with heat recovery generator of superheated steam for injecting into the combustion chamber and of saturated steam of cooling then injecting into the combustion chamber - Google Patents

Gas turbine with heat recovery generator of superheated steam for injecting into the combustion chamber and of saturated steam of cooling then injecting into the combustion chamber Download PDF

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Publication number
EP0899438A1
EP0899438A1 EP97810594A EP97810594A EP0899438A1 EP 0899438 A1 EP0899438 A1 EP 0899438A1 EP 97810594 A EP97810594 A EP 97810594A EP 97810594 A EP97810594 A EP 97810594A EP 0899438 A1 EP0899438 A1 EP 0899438A1
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EP
European Patent Office
Prior art keywords
combustion chamber
steam
gas turbine
turbine group
heat recovery
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP97810594A
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German (de)
French (fr)
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EP0899438B1 (en
Inventor
Hans Ulrich Frutschi
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Alstom SA
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ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Priority to EP19970810594 priority Critical patent/EP0899438B1/en
Priority to DE59707371T priority patent/DE59707371D1/en
Publication of EP0899438A1 publication Critical patent/EP0899438A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K21/00—Steam engine plants not otherwise provided for
    • F01K21/04—Steam engine plants not otherwise provided for using mixtures of steam and gas; Plants generating or heating steam by bringing water or steam into direct contact with hot gas
    • F01K21/047—Steam engine plants not otherwise provided for using mixtures of steam and gas; Plants generating or heating steam by bringing water or steam into direct contact with hot gas having at least one combustion gas turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to a method for operating a power plant according to Preamble of claim 1
  • water injection at a suitable point which counteracts overheating of the cooling steam, can be intervened, on the other hand, by supplying, for example, an amount of flue gas, which has a corrective action against a weak cooling effect.
  • Such provisions are always associated with additional circuitry complexity, with maximizing the efficiency having its limits in this regard.
  • the invention seeks to remedy this.
  • the invention as set out in the claims is characterized, the task is based on a method of the beginning to maximize the efficiency and performance of the system.
  • a saturated steam quantity is taken from a waste heat steam generator connected downstream of the gas turbine group and used as cooling steam for the components of this gas turbine group to be cooled.
  • the cooling is accomplished using a closed cooling path, ie all the amount of steam is introduced into the combustion chamber after the cooling path has flowed through it. With this flow, the saturated steam is heated to such an extent that it has the quality of an overheated steam when it is introduced into the high-pressure combustion chamber.
  • the remaining condensate fed into the waste heat steam generator is processed into superheated steam and fed directly into the high-pressure combustion chamber.
  • Fig. 1 shows a power plant, which from a gas turbine group, one of the Gas turbine group downstream heat recovery steam generator and one with this there is an active steam cycle.
  • the present gas turbine group is based on sequential combustion.
  • provision of the operation of the various Combustion chambers necessary fuel can, for example, by accomplishes coal gasification cooperating with the gas turbine group become.
  • it is also possible to use the one used Obtain fuel from a primary fuel network.
  • the present gas turbine group which can also act as an autonomous unit, consists of a compressor 1, a first combustion chamber 2 connected downstream of the compressor, one first turbine 3, one of these turbines 3, downstream of this combustion chamber 2 downstream second combustion chamber 4 and one of these combustion chambers 4 downstream second turbine 5.
  • the compressor 1, respectively. the compressor unit can be operatively connected to intermediate cooling.
  • the mentioned flow machines 1, 3, 5 have a uniform shaft 26. This wave is preferably mounted on two bearings that are not shown in the figure, which preferably on the head side of the compressor 1 and downstream of the second turbine 5 are placed.
  • the intake air 6 is compressed and flows in the compressor 1 then as compressed air 7 in a housing, not shown. In this case is also housed the first combustion chamber 2, which is preferably as contiguous annular combustion chamber is formed.
  • the compressed air 7 to the first combustion chamber 2 can be provided from a not shown Air storage system.
  • the annular combustion chamber 2 has distributed over the circumference, a number of burners, not shown, which are preferably designed as a premix burner. In itself, here diffusion burners are also used.
  • a number of burners not shown, which are preferably designed as a premix burner.
  • diffusion burners are also used.
  • premix burner in the circumferential direction
  • a small one between each two large premix burners Premix burner of the same configuration is available.
  • the big premix burners which have the function of main burners are entitled the small premix burners, which are the pilot burners of this combustion chamber, with respect to the burner air flowing through them, ie the compressed air 7 the compressor 1, in a size relationship to each other, which is determined on a case-by-case basis becomes.
  • the pilot burners work in the entire load range of the combustion chamber independent premix burner, whereby the air ratio remains almost constant.
  • the Zu or The main burner is switched off according to certain system-specific Requirements. Because the pilot burners run with the ideal mixture in the entire load range NOx emissions are very low even at partial load. With such a constellation, the surrounding streamlines come in the front area the ring combustion chamber very close to the vortex centers of the pilot burners, so that ignition is only possible with these pilot burners. At the The amount of fuel that is supplied via the pilot burner will start up increased until they are controlled, i.e. until the full amount of fuel is available. The configuration is chosen so that this point of the respective Load shedding conditions of the gas turbine group. The further increase in performance then takes place via the main burner. At the peak load of the The main burner is therefore also fully controlled in the gas turbine group.
  • the annular combustion chamber can consist of a number of individual tubular combustion chambers exist, which are also inclined, sometimes helical, are arranged around the rotor axis. This annular combustion chamber 2, independently from their interpretation, will and can be geometrically arranged that it has practically no influence on the rotor length.
  • the hot gases 8 from this first combustion chamber 2 act on the immediately downstream one first turbine 3, aware of its caloric relaxing effect on the hot gases is kept to a minimum, i.e. this turbine 3 is therefore no longer exist as two rows of blades. With such a turbine 3 it becomes necessary be a pressure equalization on the end faces to stabilize the axial thrust to provide.
  • the hot gases 9 partially relaxed in the turbine 3, which flow directly into the second combustion chamber 4, for the reasons stated a fairly high temperature, preferably it is specific to the company to interpret that it is still around 1000 ° C.
  • This second combustion chamber 4 has essentially the shape of a coherent annular axial or quasi-axial ring cylinder.
  • This combustion chamber 4 can of course also from a number axially, quasi-axially or helically arranged and exist in self-contained combustion chambers.
  • Combustion chamber 4 consisting of a single combustion chamber, so are circumferential and radial of this annular cylinder several in the Figure fuel lances not shown dispatched.
  • This combustion chamber 4th has no burner: the combustion of one coming from the turbine 3 partially relaxed hot gases 9 injected fuel 13 happens here by self-ignition, as far as the temperature level of such an operating mode allows.
  • the partially relaxed hot gases 9 from the turbine 3 may still be very high, such as set out above around 1000 ° C, and of course also at partial load operation, which plays a causal role in the design of this turbine 2.
  • a gaseous Fuel for example natural gas
  • the partially relaxed hot gases 9 from the turbine 3 may still be very high, such as set out above around 1000 ° C, and of course also at partial load operation, which plays a causal role in the design of this turbine 2.
  • the Flame front remains locally stable.
  • this combustion chamber 4 preferably arranged in the circumferential direction on the inner and outer walls, a number of elements not shown are provided, which in Axial direction are preferably placed upstream of the fuel lances.
  • the task of these elements is to create vortices which have a backflow zone, analogue to induce that in the premixing burners already mentioned. Since it is in this combustion chamber 4, due to the axial arrangement and the length, is a high-speed combustion chamber, in which the average speed of the working gases is greater than approx. 60 m / s vortex-generating elements are designed to conform to the flow. Inflow side these should preferably have a tetrahedral shape with inclined flow Areas exist.
  • the vortex generating elements can be placed either on the outer surface and / or on the inner surface. Of course the vortex generating elements can also be shifted axially to one another be.
  • the downstream surface of the vortex generating elements is essentially radial, so that a backflow zone is established from there.
  • the auto-ignition in the combustion chamber 4 must also be in the transient Load ranges as well as in the partial load range of the gas turbine group secured remain, i.e. auxiliary measures must be provided which Ensure auto-ignition in the combustion chamber 4 even if there is one Flexion of the temperature of the gases in the area of the fuel injection should stop. In order to safely ignite the injected into the combustion chamber 4 To ensure gaseous fuel, this becomes a small one Amount of another fuel with a lower ignition temperature added. For example, fuel oil is very suitable as an auxiliary fuel.
  • liquid auxiliary fuel injected accordingly, fulfills the task, so to speak to act as a fuse, and then also enables self-ignition in the Combustion chamber 4 when the partially relaxed hot gases 9 from the first turbine 3 have a temperature below the desired optimal level of 1000 ° C should.
  • fuel oil to ensure auto-ignition Providing proves to be particularly appropriate when the Gas turbine group is operated with a greatly reduced load.
  • This precaution bears furthermore crucially to ensure that the combustion chamber 4 has a minimal may have axial length. The short length of the combustion chamber 4, the effect of the vortex generating elements for flame stabilization as well as the ongoing Ensuring auto-ignition is therefore responsible for that the combustion takes place very quickly, and the residence time of the fuel in the Area of the hot flame front remains minimal.
  • the second is between the outflow plane of the first turbine 3 and the flow plane of the second turbine 5 Combustion chamber 4 has a minimum length.
  • a gas turbine group can be made using only 1 or 2 rows of blades provide whose rotor shaft 26 is technically due to its minimized length is perfectly supported on two bearings.
  • the power output of the turbomachines happens via a generator connected to the compressor 27, which can also serve as a starting motor.
  • the heat recovery steam generator 14 After relaxation in the turbine 5 flow through the exhaust gases, which still have a high caloric potential 11 the heat recovery steam generator 14 already mentioned, in which in heat exchange processes steam is generated in various ways, which is then the medium for the operation of this power plant.
  • the calorific used exhaust gases 11 then flow outside as flue gases 25.
  • the waste heat steam generator 14 consists of an economizer 14c, an evaporator 14b and a superheater 14a.
  • a pump 15 is used to convey water 16 poured into the economizer 14c, in which in the heat exchange process with the exhaust gases flowing through there a first heating of the pumped water takes place, the hot water 17 formed here being passed into a drum 28 becomes.
  • This hot water 17 is then discharged from the drum 28 via a line 18 removed and for further thermal treatment by the medium pressure part 14b passed in the heat recovery steam generator 14. This produces a saturated steam 19 which is returned to the drum 28.
  • a portion 22 of this is called the amount of cooling steam passed into the components of the gas turbine group to be cooled, the other
  • the amount of steam 20 undergoes a further heating to superheated in the high-pressure part 14a Steam 21, which is fed directly into the high-pressure combustion chamber 2.
  • This The feed line can also be indirectly via a steam turbine, not shown, preferably a back pressure steam turbine.
  • the removed for cooling purposes Amount of steam 22 from the drum 28 is closed over individual Flow paths 22a / 23a, 22b / 23b, 22c / 23c, 22d, / 23d through the ones to be cooled Components 2, 3, 4, 5 passed, this steam then also into the high-pressure combustion chamber 2 is entered.
  • the removal of saturated steam 22 from the drum 28 can also be from another point in the steam cycle manage where there is a sufficiently high pressure.
  • Such a precaution can be used, for example, wherever the heat recovery steam generator consists of an impression kettle. If handled correctly, this can be done Circuit, including a throttle body integrated in line 21 24, so that the two introduced into the high pressure combustion chamber 2 Amounts of steam 21, 23 have approximately the same quality, which is thereby maximizing the efficiency and specific performance of the system can be achieved.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

The heat recovery process involves producing superheated steam (21) in an exhaust heat steam generator (14). This steam is introduced into the high-pressure combustion chamber of the gas turbine group. Saturated steam is taken from a drum (28) of the exhaust heat steam generator via closed flow paths (22a/23a, 22b/23b, 22c/23c, 22d, 23d) and sent through the components (2, 3, 4, 5) of the gas turbine group which require cooling.

Description

Technisches GebietTechnical field

Die Erfindung betrifft ein Verfahren zum Betrieb einer Kraftwerksanlage gemäss Oberbegriff des Anspruch 1The invention relates to a method for operating a power plant according to Preamble of claim 1

Stand der TechnikState of the art

Aus DE-A1-44 09 567 ist ein Verfahren zur Kühlung thermisch belasteter Komponenten einer Gasturbine bekanntgeworden, bei welchem eine bestimmte Sattdampfmenge aus einem der Gasturbogruppe nachgeschalteten entnommen wird. Vorzugsweise stammt diese Dampfmenge aus einer zum Dampfkreislauf gehörenden Trommel. Bei den mit Sattdampf zu kühlenden Komponenten handelt es sich vorzugsweise um die Brennkammer und Turbine, welche gekühlt werden. Nach erfolgter Kühlung der genannten Komponenten ist die Dampfmenge soweit überhitzt worden, so dass sie dann arbeitsleistend in eine Dampfturbine an passender Stelle eingeleitet werden kann.
Bei einer solchen Schaltung stellt man immer wieder fest, dass es aus Sicherheitsgründen vorteilhaft ist, Vorkehrungen vorzusehen, welche die Kühlwirkung der angezapften Dampfmenge nach oben oder nach unten zu korrigieren vermögen. Einerseits kann durch Wassereinspritzung an geeigneter Stelle, welche einer Ueberhitzung des Kühldampfes entgegenwirkt, andererseits durch Zuführung bei-spielsweise einer Rauchgasmenge, welche korrigierend gegen eine zu schwache Kühlwirkung einwirkt, eingegriffen werden.
Solche Beistellungen sind immer mit einem zusätzlichen schaltungstechnischen Aufwand verbunden, wobei eine Maximierung des Wirkungsgrads seine diesbezüglichen Grenzen aufweist.From DE-A1-44 09 567 a method for cooling thermally loaded components of a gas turbine has become known, in which a certain amount of saturated steam is taken from a downstream of the gas turbine group. This amount of steam preferably comes from a drum belonging to the steam cycle. The components to be cooled with saturated steam are preferably the combustion chamber and turbine, which are cooled. After the above components have been cooled, the amount of steam has been overheated to such an extent that it can then be introduced into a steam turbine at a suitable point to perform the work.
With such a circuit, it is repeatedly found that, for safety reasons, it is advantageous to take precautions which are able to correct the cooling effect of the tapped amount of steam upwards or downwards. On the one hand, water injection at a suitable point, which counteracts overheating of the cooling steam, can be intervened, on the other hand, by supplying, for example, an amount of flue gas, which has a corrective action against a weak cooling effect.
Such provisions are always associated with additional circuitry complexity, with maximizing the efficiency having its limits in this regard.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, liegt die Aufgabe zugrunde bei einem Verfahren der eingangs genannten Art den Wirkungsgrad und die Leistung der Anlage zu maximieren.The invention seeks to remedy this. The invention as set out in the claims is characterized, the task is based on a method of the beginning to maximize the efficiency and performance of the system.

Dies wird erreicht, indem die ganze im Zusammenhang mit dem Betrieb der Gasturbogruppe erzeugte Dampfmenge vor der Befeuerung einer zur Gasturbogruppe gehörenden Hochdruck-Brennkammer eingebracht wird.This is achieved by the whole of the operation of the Gas turbine group generated amount of steam before firing one to the gas turbine group belonging high-pressure combustion chamber is introduced.

Dabei wird eine Sattdampfmenge aus einem der Gasturbogruppe nachgeschalteten Abhitzedampferzeuger entnommen und als Kühldampf für die zu kühlenden Komponenten dieser Gasturbogruppe verwendet. Die Kühlung wird hierbei anhand eines geschlossenen Kühlungspfad bewerkstelligt, d.h. sämtliche Dampfmenge wird nach durchströmtem Kühlungspfad in die Brennkammer eingebracht. Bei dieser Durchströmung wird der Sattdampf soweit erhitzt, dass er bei der Einleitung in die Hochdruck-Brennkammer die Qualität eines überhitzten Dampfes aufweist.
Das restliche in den Abhitzedampferzeuger eingespeiste Kondensat wird zu überhitztem Dampf aufbereitet und direkt in die Hochdruck-Brennkammer eingeleitet.
Somit wird der Hochdruck-Brennkammer sämtlicher in dem Abhitzedampferzeuger produzierter Dampf zugeführt, wobei die Qualität annähernd gleichförmig ist, d.h.die Kühlung der thermisch beanspruchten Komponenten der Gasturbogruppe bewirken eine qualitative Erhöhung des anfänglich eingeleiteten Sattdampfes. Indem diese Teilmenge über die Kühlung thermisch aufbereitet wird, steht für die restliche in dem Abhitzedampferzeuger aufzubereitende Dampfmenge mehr Wärmepotential zur Verfügung, so dass schliesslich der Hochdruck-Brennkammer eine grössere qualitätiv hochstehende Dampfmenge zur Verfügung steht. Einerseits wird damit der Wirkungsgrad maximiert, andererseits nimmt die spezifische Leistung der Anlage durch ebendiese grössere und bessere Dampfmenge zu.A saturated steam quantity is taken from a waste heat steam generator connected downstream of the gas turbine group and used as cooling steam for the components of this gas turbine group to be cooled. The cooling is accomplished using a closed cooling path, ie all the amount of steam is introduced into the combustion chamber after the cooling path has flowed through it. With this flow, the saturated steam is heated to such an extent that it has the quality of an overheated steam when it is introduced into the high-pressure combustion chamber.
The remaining condensate fed into the waste heat steam generator is processed into superheated steam and fed directly into the high-pressure combustion chamber.
All of the steam produced in the waste heat steam generator is thus fed to the high-pressure combustion chamber, the quality being approximately uniform, ie the cooling of the thermally stressed components of the gas turbine group brings about a qualitative increase in the initially introduced saturated steam. Because this partial quantity is thermally processed via cooling, more heat potential is available for the remaining quantity of steam to be processed in the waste heat steam generator, so that finally a larger, high-quality quantity of steam is available to the high-pressure combustion chamber. On the one hand, the efficiency is maximized, on the other hand, the specific performance of the system increases due to this larger and better amount of steam.

Vorteilhafte und zweckmässige Weiterbildungen der erfindungsgemässen Aufgabenlösung sind in den weiteren Ansprüchen gekennzeichnet.Advantageous and expedient developments of the task solution according to the invention are characterized in the further claims.

Im folgenden wird anhand der Zeichnung ein Ausführungsbeispiel der Erfindung näher erläutert. Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind fortgelassen worden. Die Strömungsrichtung der verschiedenen medien ist mit Pfeilen angegeben.In the following, an embodiment of the invention is based on the drawing explained in more detail. All not necessary for the immediate understanding of the invention Elements have been left out. The flow direction of the different media is indicated by arrows.

Kurze Beschreibung der ZeichnungBrief description of the drawing

  • Die einzige Figur zeigt eine Schaltung einer Gasturbogruppe in Wirkvwerbindung mit einem nachgeschalteten Abhitzedampferzeuger und dessen Infrastruktur.The only figure shows a circuit of a gas turbine group in active connection with a downstream heat recovery steam generator and its infrastructure.

    • Wege zur Ausführung der Erfindung, gewerbliche VerwendbarkeitWAYS OF CARRYING OUT THE INVENTION, INDUSTRIAL APPLICABILITY

    Fig. 1 zeigt eine Kraftwerksanlage, welche aus einer Gasturbogruppe, einem der Gasturbogruppe nachgeschalteten Abhitzedampferzeuger und einem mit diesem in Wirkverbindung stehenden Dampfkreislauf besteht. Fig. 1 shows a power plant, which from a gas turbine group, one of the Gas turbine group downstream heat recovery steam generator and one with this there is an active steam cycle.

    Die vorliegende Gasturbogruppe ist auf einer sequentiellen Verbrennung aufgebaut. Die in der Figur nicht ersichtliche Bereitstellung des zum Betrieb der verschiedenen Brennkammern notwendigen Brennstoffes kann beispielsweise durch eine mit der Gasturbogruppe zusammenwirkende Kohlenvergasung bewerkstelligt werden. Selbstverständlich ist es auch möglich, den zum Einsatz gelangenden Brennstoff aus einem Brennstoff-Primärnetz zu beziehen. Wird die Versorgung eines gasförmigen Brennstoffes zum Betrieb der Gasturbogruppe über eine Pipeline bereitgestellt, so kann das Potential aus der Druck- und/oder Temperaturdifferenz zwischen Primärnetz und Verbrauchernetz für die Belange der Gasturbogruppe oder allgemein der Schaltung rekuperiert werden. Die vorliegende Gasturbogruppe, die auch als autonome Einheit wirken kann, besteht aus einem Verdichter 1, einer dem Verdichter nachgeschalteten ersten Brennkammer 2, einer dieser Brennkammer 2 nachgeschalteten ersten Turbine 3, einer dieser Turbine 3 nachgeschalteten zweiten Brennkammer 4 und einer dieser Brennkammer 4 nachgeschalteten zweiten Turbine 5. Der Verdichter 1 resp. die Verdichtereinheit kann mit einer Zwischenkühlung in Wirkverbindung stehen. Die genannten Strömungsmaschinen 1, 3, 5 weisen eine einheitliche Welle 26 auf. Diese Welle ist vorzugsweise auf zwei in der Figur nicht näher ersichtlichen Lagern gelagert, welche vorzugsweise kopfseitig des Verdichters 1 und stromab der zweiten Turbine 5 plaziert sind. Die angesaugte Luft 6 wird im Verdichter 1 komprimiert und strömt dann als verdichtete Luft 7 in ein nicht näher gezeigtes Gehäuse. In diesem Gehäuse ist auch die erste Brennkammer 2 untergebracht, welche vorzugsweise als zusammenhängende Ringbrennkammer ausgebildet ist. Selbsverständlich kann die verdichtete Luft 7 zur ersten Brennkammer 2 aus einer nicht gezeigten Luftspeicheranlage beigestellt werden. Die Ringbrennkammer 2 weist kopfseitig, auf den Umfang verteilt, eine Anzahl von nicht näher gezeigten Brennern auf, welche vorzugsweise als Vormischbrenner ausgelegt sind. An sich können hier auch Diffusionsbrenner zum Einsatz gelangen. Im Sinne einer Reduzierung der Schadstoff-Emissionen aus dieser Verbrennung, insbesondere was die NOx-Emissionen betrifft, ist es indessen vorteilhaft, eine Anordnung von Vormischbrennern gemäss EP-PS-0 321 809 vorzusehen, wobei der Erfindungsgegenstand aus der genannten Druckschrift integrierender Bestandteil dieser Beschreibung ist, darüber hinaus auch die dort beschriebene Art der Zuführung der verschiedenen Brennstoffe. Was die Anordnung der Vormischbrenner in Umfangsrichtung der Ringbrennkammer 2 anbelangt, so kann eine solche bei Bedarf von der üblichen Konfiguration gleicher Brenner abweichen, und stattdessen können unterschiedlich grosse Vormischbrenner zum Einsatz kommen. Dies geschieht vorzugsweise so, dass jeweils zwischen zwei grossen Vormischbrennern ein kleiner Vormischbrenner gleicher Konfiguration disponiert ist. Die grossen Vormischbrenner, welche die Funktion von Hauptbrennern zu erfüllen haben, stehen zu den kleinen Vormischbrennern, welche die Pilotbrenner dieser Brennkammer sind, bezüglich der sie durchströmenden Brennerluft, also der verdichteten Luft 7 aus dem Verdichter 1, in einem Grössenverhältnis zueinander, das fallweise festgelegt wird. Im gesamten Lastbereich der Brennkammer arbeiten die Pilotbrenner als selbstgängige Vormischbrenner, wobei die Luftzahl fast konstant bleibt. Die Zu- oder Abschaltung der Hauptbrenner erfolgt nach bestimmten anlagespezifischen Vorgaben. Weil die Pilotbrenner im ganzen Lastbereich bei idealem Gemisch gefahren werden können, sind die NOx-Emissionen auch bei Teillast sehr gering. Bei einer solchen Konstellation kommen die umlaufenden Stromlinien im Frontbereich der Ringbrennkammer sehr nahe an die Wirbelzentren der Pilotbrenner heran, so dass eine Zündung an sich nur mit diesen Pilotbrennern möglich ist. Beim Hochfahren wird die Brennstoffmenge, die über die Pilotbrenner zugeführt wird, soweit gesteigert, bis diese ausgesteuert sind, d.h. bis die volle Brennstoffmenge zur Verfügung steht. Die Konfiguration wird so gewählt, dass dieser Punkt der jeweiligen Lastabwurfbedingungen der Gasturbogruppe entspricht. Die weitere Leistungssteigerung erfolgt dann über die Hauptbrenner. Bei der Spitzenlast der Gasturbogruppe sind sonach auch die Hauptbrenner voll ausgesteuert. Weil die durch die Pilotbrenner initiierte Konfiguration "kleiner" heisser Wirbelzentren zwischen den von den Hauptbrennern stammenden "grossen" kühleren Wirbelzentren extrem instabil ausfällt, wird auch bei mager betriebenen Hauptbrennern im Teillastbereich ein sehr guter Ausbrand mit zusätzlich zu den NOx-Emissionen niedrigen CO- und UHC-Emissionen erreicht, d.h. die heissen Wirbel der Pilotbrenner dringen sofort in die kleinen Wirbel der Hauptbrenner ein. Selbstverständlich kann die Ringbrennkammer aus einer Anzahl einzelner rohrförmiger Brennräume bestehen, welche ebenfalls schrägringförmig, bisweilen auch schraubenförmig, um die Rotorachse angeordnet sind. Diese Ringbrennkammer 2, unabhängig von ihrer Auslegung, wird und kann geometrisch so angeordnet werden, dass sie auf die Rotorlänge praktisch keinen Einfluss ausübt. Die Heissgasen 8 aus dieser ersten Brennkammer 2 beaufschlagen die unmittelbar nachgeschaltete erste Turbine 3, deren kalorisch entspannende Wirkung auf die Heissgase bewusst minimal gehalten wird, d.h. diese Turbine 3 wird demnach aus nicht mehr als zwei Laufschaufelreihen bestehen. Bei einer solchen Turbine 3 wird es nötig sein, einen Druckausgleich an den Stirnflächen zwecks Stabilisierung des Axialschubes vorzusehen. Die in der Turbine 3 teilentspannten Heissgase 9, welche unmittelbar in die zweite Brennkammer 4 strömen, weisen aus dargelegten Grün-den eine recht hohe Temperatur auf, vorzugsweise ist sie betriebsspezifisch so auszulegen, dass sie sicher noch um 1000°C beträgt. Diese zweite Brennkammer 4 hat im wesentlichen die Form eines zusammenhängenden ringförmigen axialen oder quasi-axialen Ringzylinders. Diese Brennkammer 4 kann selbstverständlich auch aus einer Anzahl axial, quasi-axial oder schraubenförmig angeordneten und in sich abgeschlossenen Brennräumen bestehen. Was die Konfiguration der ringförmigen, aus einem einzigen Brennraum bestehenden Brennkammer 4 betrifft, so sind in Umfangsrichtung und radial dieses ringförmigen Zylinders mehrere in der Figur nicht näher gezeigte Brennstofflanzen disponiert. Diese Brennkammer 4 weist keinen Brenner auf: Die Verbrennung eines in die aus der Turbine 3 kommenden teilentspannten Heissgase 9 eingedüsten Brennstoffes 13 geschieht hier durch Selbstzündung, soweit freilich das Temperaturniveau eine solche Betriebsart zulässt. Ausgehend davon, dass die Brennkammer 4 mit einem gasförmigen Brennstoff, also beispielsweise Erdgas, betrieben wird, muss die Austrittstemperatur der teilentspannten Heissgase 9 aus der Turbine 3 noch sehr hoch sein, wie oben dargelegt um die 1000°C, und dies selbstverständlich auch bei Teillastbetrieb, was auf die Auslegung dieser Turbine 2 eine ursächliche Rolle spielt. Um die Betriebssicherheit und einen hohen Wirkungsgrad bei einer auf Selbstzündung ausgelegten Brennkammer zu gewährleisten, ist es eminent wichtig, dass die Flammenfront ortsmässig stabil bleibt. Zu diesem Zweck werden in dieser Brennkammer 4, vorzugsweise an der Innen- und Aussenwand in Umfangsrichtung disponiert, eine Reihe von nicht näher gezeigten Elementen vorgesehen, welche in axialer Richtung vorzugsweise stromauf der Brennstofflanzen plaziert sind. Die Aufgabe dieser Elemente besteht darin, Wirbel zu erzeugen, welche eine Rückströmzone, analog derjenige in den bereits erwähnten Vormischbrennern, induzieren. Da es sich bei dieser Brennkammer 4, aufgrund der axialen Anordnung und der Baulänge, um eine Hochgeschwindigkeitsbrennkammer handelt, bei welcher die mittlere Geschwindigkeit der Arbeitsgase grösser ca. 60 m/s ist, müssen die wirbelerzeugenden Elemente strömungskonform ausgebildet werden. Anströmungsseitig sollen diese vorzugsweise aus einer tetraederförmigen Form mit anströmungsschiefen Flächen bestehen. Die wirbelerzeugenden Elemente können entweder an der Aussenfläche und/oder an der Innenfläche plaziert sein. Selbstverständlich können die wirbelerzeugenden Elemente auch axial zueinander verschoben sein. Die abströmungsseitige Fläche der wirbelerzeugenden Elemente ist im wesentlichen radial ausgebildet, so dass sich ab dort eine Rückströmzone einstellt. Die Selbstzündung in der Brennkammer 4 muss indessen auch in den transienten Lastbereichen sowie im Teillastbereich der Gasturbogruppe gesichert bleiben, d.h., es müssen Hilfsvorkehrungen vorgesehen werden, welche die Selbstzündung in der Brennkammer 4 auch dann sicherstellen, wenn sich eine Flexion der Temperatur der Gase im Bereich der Eindüsung des Brennstoffes einstellen sollte. Um eine sichere Selbstzündung des in die Brennkammer 4 eingedüsten gasförmigen Brennstoffes zu gewährleisten, wird diesem eine kleine Menge eines anderen Brennstoffes mit einer niedrigeren Zündtemperatur beigegeben. Als Hilfsbrennstoff eignet sich hier beispielsweise Brennöl sehr gut. Der flüssige Hilfsbrennstoff, entsprechend eingedüst, erfüllt die Aufgabe, sozusagen als Zündschnur zu wirken, und ermöglicht auch dann eine Selbstzündung in der Brennkammer 4, wenn die teilentspannten Heissgase 9 aus der ersten Turbine 3 eine Temperatur unterhalb des angestrebten optimalen Niveaus von 1000°C aufweisen sollten. Diese Vorkehrung, Brennöl zur Sicherstellung einer Selbstzündung vorzusehen, erweist sich freilich immer dann als besonders angebracht, wenn die Gasturbogruppe mit stark reduzierter Last betrieben wird. Diese Vorkehrung trägt des weiteren entscheidend dazu bei, dass die Brennkammer 4 eine minimale axiale Länge aufweisen kann. Die kurze Baulänge der Brennkammer 4, die Wirkung der wirbelerzeugenden Elemente zur Flammenstabilisierung sowie die fort-währende Sicherstellung der Selbstzündung sind demnach dafür verantwortlich, dass die Verbrennung sehr rasch erfolgt, und die Verweilzeit des Brennstoffes im Bereich der heissen Flammenfront minimal bleibt. Eine unmittelbar verbrennungsspezifisch messbare Wirkung hieraus betrifft die NOx-Emissionen, welche eine Minimierung erfahren, dergestalt, dass sie nunmehr kein Thema mehr bilden. Diese Ausgangslage ermöglicht ferner, den Ort der Verbrennung klar zu definieren, was sich in einer optimierten Kühlung der Strukturen dieser Brennkammer 4 niederschlägt. Die in der Brennkammer 4 aufbereiteten Heissgase 10 beaufschlagen anschliessend eine nachgeschaltete zweite Turbine 5. Die thermodynamischen Kennwerte der Gasturbogruppe können so ausgelegt werden, dass die Abgase 11 aus der zweiten Turbine 5 noch soviel kalorisches Potential aufweisen, um damit eine hier anhand eines Abhitzedampferzeugers 14 dargestellte Dampferzeugungsstufe und Dampfkreislauf zu betreiben. Wie bereits bei der Beschreibung der Ringbrennkammer 2 hingewiesen wurde, ist diese geometrisch so angeordnet, dass sie auf die Rotorlänge der Gasturbogruppe praktisch keinen Einfluss ausübt. Des weiteren ist feststellbar, dass die zweite zwischen Abströmungsebene der ersten Turbine 3 und Anströmungsebene der zweiten Turbine 5 verlaufende Brennkammer 4 eine minimale Länge aufweist. Da ferner die Entspannung der Heissgase in der ersten Turbine 3, aus dargelegten Gründen, über wenige, vorzugsweise über nur 1 bis 2 Laufschaufelreihen erfolgt, lässt sich eine Gasturbogruppe bereitstellen, deren Rotorwelle 26 aufgrund ihrer minimierten Länge technisch einwandfrei auf zwei Lagern abstützbar ist. Die Leistungsabgabe der Strömungsmaschinen geschieht über einen verdichterseitig angekoppelten Generator 27, der auch als Anwurfmotor dienen kann. Nach Entspannung in der Turbine 5 durchströmen die noch mit einem hohen kalorischen Potential versehenen Abgase 11 den bereits erwähnten Abhitzedampferzeuger 14, in welchem in Wärmetauschverfahren verschiedentlich Dampf erzeugt wird, der dann das Medium für die Betriebsweise dieser Kraflwerksanlage bildet. Die kalorisch genutzten Abgase 11 strömen anschliessend als Rauchgase 25 ins Freie.The present gas turbine group is based on sequential combustion. The not visible in the figure provision of the operation of the various Combustion chambers necessary fuel can, for example, by accomplishes coal gasification cooperating with the gas turbine group become. Of course, it is also possible to use the one used Obtain fuel from a primary fuel network. Will the supply of a gaseous fuel for operating the gas turbine group via a pipeline provided, so the potential from the pressure and / or temperature difference between the primary network and the consumer network for the interests of the gas turbine group or generally be recuperated from the circuit. The present gas turbine group, which can also act as an autonomous unit, consists of a compressor 1, a first combustion chamber 2 connected downstream of the compressor, one first turbine 3, one of these turbines 3, downstream of this combustion chamber 2 downstream second combustion chamber 4 and one of these combustion chambers 4 downstream second turbine 5. The compressor 1, respectively. the compressor unit can be operatively connected to intermediate cooling. The mentioned flow machines 1, 3, 5 have a uniform shaft 26. This wave is preferably mounted on two bearings that are not shown in the figure, which preferably on the head side of the compressor 1 and downstream of the second turbine 5 are placed. The intake air 6 is compressed and flows in the compressor 1 then as compressed air 7 in a housing, not shown. In this case is also housed the first combustion chamber 2, which is preferably as contiguous annular combustion chamber is formed. Of course can the compressed air 7 to the first combustion chamber 2 from a not shown Air storage system can be provided. The annular combustion chamber 2 has distributed over the circumference, a number of burners, not shown, which are preferably designed as a premix burner. In itself, here diffusion burners are also used. In the sense of reducing the Pollutant emissions from this combustion, especially what the NOx emissions , however, it is advantageous to have an arrangement of premix burners to provide according to EP-PS-0 321 809, the subject of the invention from the cited publication an integral part of this description is, moreover, the type of feeding of the various types described there Fuels. As for the arrangement of the premix burner in the circumferential direction As far as the ring combustion chamber 2 is concerned, such a deviate from the usual configuration of the same burner, and instead can premix burners of different sizes are used. this happens preferably such that a small one between each two large premix burners Premix burner of the same configuration is available. The big premix burners, which have the function of main burners are entitled the small premix burners, which are the pilot burners of this combustion chamber, with respect to the burner air flowing through them, ie the compressed air 7 the compressor 1, in a size relationship to each other, which is determined on a case-by-case basis becomes. The pilot burners work in the entire load range of the combustion chamber independent premix burner, whereby the air ratio remains almost constant. The Zu or The main burner is switched off according to certain system-specific Requirements. Because the pilot burners run with the ideal mixture in the entire load range NOx emissions are very low even at partial load. With such a constellation, the surrounding streamlines come in the front area the ring combustion chamber very close to the vortex centers of the pilot burners, so that ignition is only possible with these pilot burners. At the The amount of fuel that is supplied via the pilot burner will start up increased until they are controlled, i.e. until the full amount of fuel is available. The configuration is chosen so that this point of the respective Load shedding conditions of the gas turbine group. The further increase in performance then takes place via the main burner. At the peak load of the The main burner is therefore also fully controlled in the gas turbine group. Because the configuration of "small" hot vortex centers initiated by the pilot burner the "big" cooler vortex centers from the main distillers turns out to be extremely unstable, even with lean burners in the Part load range a very good burnout with in addition to the NOx emissions achieved low CO and UHC emissions, i.e. the hot eddies of the pilot burner immediately penetrate the small swirls of the main burner. Of course the annular combustion chamber can consist of a number of individual tubular combustion chambers exist, which are also inclined, sometimes helical, are arranged around the rotor axis. This annular combustion chamber 2, independently from their interpretation, will and can be geometrically arranged that it has practically no influence on the rotor length. The hot gases 8 from this first combustion chamber 2 act on the immediately downstream one first turbine 3, aware of its caloric relaxing effect on the hot gases is kept to a minimum, i.e. this turbine 3 is therefore no longer exist as two rows of blades. With such a turbine 3 it becomes necessary be a pressure equalization on the end faces to stabilize the axial thrust to provide. The hot gases 9 partially relaxed in the turbine 3, which flow directly into the second combustion chamber 4, for the reasons stated a fairly high temperature, preferably it is specific to the company to interpret that it is still around 1000 ° C. This second combustion chamber 4 has essentially the shape of a coherent annular axial or quasi-axial ring cylinder. This combustion chamber 4 can of course also from a number axially, quasi-axially or helically arranged and exist in self-contained combustion chambers. As for the configuration of the annular, Combustion chamber 4 consisting of a single combustion chamber, so are circumferential and radial of this annular cylinder several in the Figure fuel lances not shown dispatched. This combustion chamber 4th has no burner: the combustion of one coming from the turbine 3 partially relaxed hot gases 9 injected fuel 13 happens here by self-ignition, as far as the temperature level of such an operating mode allows. Assuming that the combustion chamber 4 with a gaseous Fuel, for example natural gas, is operated at the outlet temperature the partially relaxed hot gases 9 from the turbine 3 may still be very high, such as set out above around 1000 ° C, and of course also at partial load operation, which plays a causal role in the design of this turbine 2. To the Operational safety and a high degree of efficiency with a self-ignition To ensure that the combustion chamber is designed, it is extremely important that the Flame front remains locally stable. For this purpose, in this combustion chamber 4, preferably arranged in the circumferential direction on the inner and outer walls, a number of elements not shown are provided, which in Axial direction are preferably placed upstream of the fuel lances. The The task of these elements is to create vortices which have a backflow zone, analogue to induce that in the premixing burners already mentioned. Since it is in this combustion chamber 4, due to the axial arrangement and the length, is a high-speed combustion chamber, in which the average speed of the working gases is greater than approx. 60 m / s vortex-generating elements are designed to conform to the flow. Inflow side these should preferably have a tetrahedral shape with inclined flow Areas exist. The vortex generating elements can be placed either on the outer surface and / or on the inner surface. Of course the vortex generating elements can also be shifted axially to one another be. The downstream surface of the vortex generating elements is essentially radial, so that a backflow zone is established from there. However, the auto-ignition in the combustion chamber 4 must also be in the transient Load ranges as well as in the partial load range of the gas turbine group secured remain, i.e. auxiliary measures must be provided which Ensure auto-ignition in the combustion chamber 4 even if there is one Flexion of the temperature of the gases in the area of the fuel injection should stop. In order to safely ignite the injected into the combustion chamber 4 To ensure gaseous fuel, this becomes a small one Amount of another fuel with a lower ignition temperature added. For example, fuel oil is very suitable as an auxiliary fuel. Of the liquid auxiliary fuel, injected accordingly, fulfills the task, so to speak to act as a fuse, and then also enables self-ignition in the Combustion chamber 4 when the partially relaxed hot gases 9 from the first turbine 3 have a temperature below the desired optimal level of 1000 ° C should. This precaution, fuel oil to ensure auto-ignition Providing proves to be particularly appropriate when the Gas turbine group is operated with a greatly reduced load. This precaution bears furthermore crucially to ensure that the combustion chamber 4 has a minimal may have axial length. The short length of the combustion chamber 4, the effect of the vortex generating elements for flame stabilization as well as the ongoing Ensuring auto-ignition is therefore responsible for that the combustion takes place very quickly, and the residence time of the fuel in the Area of the hot flame front remains minimal. An immediate combustion specific measurable effect from this concerns the NOx emissions, which a Experience minimization in such a way that they are no longer an issue. This Starting position also enables the location of the combustion to be clearly defined, which is reflected in an optimized cooling of the structures of this combustion chamber 4. The hot gases 10 treated in the combustion chamber 4 are charged then a downstream second turbine 5. The thermodynamic Characteristic values of the gas turbine group can be designed such that the exhaust gases 11 from the second turbine 5 still have so much caloric potential in order to use them a steam generation stage shown here using a heat recovery steam generator 14 and operate the steam cycle. As in the description the ring combustion chamber 2, this is geometrically arranged so that they have practically no influence on the rotor length of the gas turbine group exercises. It can also be ascertained that the second is between the outflow plane of the first turbine 3 and the flow plane of the second turbine 5 Combustion chamber 4 has a minimum length. Furthermore, since the relaxation of the Hot gases in the first turbine 3, for a few reasons, are preferred, preferably A gas turbine group can be made using only 1 or 2 rows of blades provide whose rotor shaft 26 is technically due to its minimized length is perfectly supported on two bearings. The power output of the turbomachines happens via a generator connected to the compressor 27, which can also serve as a starting motor. After relaxation in the turbine 5 flow through the exhaust gases, which still have a high caloric potential 11 the heat recovery steam generator 14 already mentioned, in which in heat exchange processes steam is generated in various ways, which is then the medium for the operation of this power plant. The calorific used exhaust gases 11 then flow outside as flue gases 25.

    Der Abhitzedampferzeuger 14 besteht aus einem Economizer 14c, einem verdampfer 14b und einem Ueberhitzer 14a. Ueber eine Pumpe 15 wird Förderwasser 16 in den Economizer 14c eingeleiet, in welchem im Wärmetauschverfahren mit den dort durchströmenden Abgase eine erste Erwärmung des Förderwassers stattfindet, wobei das hier gebildete Heisswasser 17 in eine Trommel 28 geleitet wird. Dieses Heisswasser 17 wird dann über eine Leitung 18 aus der Trommel 28 entnommen und zur weiteren thermischen Aufbereitung durch den Mitteldruckteil 14b im Abhitzedampferzeuger 14 geleitet. Hieraus entsteht ein Sattdampf 19, der in die Trommel 28 rückgeführt wird. Eine Teil 22 davon wird als Kühldampfmenge in die zu kühlenden Komponenten der Gasturbogruppe geleitet, die andere Dampfmenge 20 erfährt im Hochdruckteil 14a eine weitere Aufheizung zu überhitztem Dampf 21, der direkt in die Hochdruck-Brennkammer 2 geleitet wird. Diese Zuleitung kann auch mittelbar über eine nicht näher gezeigte Dampfturbine, vorzugsweise eine Gegendruckdampfturbine erfolgen. Die zu Kühlzwecken entnommene Dampfmenge 22 aus der Trommel 28 wird über einzelne geschlossene Strömungspfade 22a/23a, 22b/23b, 22c/23c, 22d,/23d durch die zu kühlenden Komponenten 2, 3, 4, 5 geleitet, wobei dieser Dampf dann ebenfalls in die Hochdruck-Brennkammer 2 eingegeben wird. Die Entnahme des Sattdampfes 22 aus der Trommel 28 lässt sich auch aus einer anderen Stelle des Dampfkreislaufes bewerkstelligen, wo ein genügend hoher Druck vorherrscht. Eine solche Vorkehrung lässt sich beispielsweise immer dort anwenden, wo der Abhitzedampferzeuger aus einem Eindruckkessel besteht. Bei richtiger Handhabung lässt sich diese Schaltung, unter Einbeziehung eines in die Leitung 21 integrierten Drosselorgans 24, so auslegen, dass die beiden in die Hochdruck-Brennkammer 2 eingeleiteten Dampfmengen 21, 23 annähernd dieselbe Qualität aufweisen, womit sich dadurch eine Maximierung des Wirkungsgrades und der spezifischen Leistung der Anlage erreichen lässt.The waste heat steam generator 14 consists of an economizer 14c, an evaporator 14b and a superheater 14a. A pump 15 is used to convey water 16 poured into the economizer 14c, in which in the heat exchange process with the exhaust gases flowing through there a first heating of the pumped water takes place, the hot water 17 formed here being passed into a drum 28 becomes. This hot water 17 is then discharged from the drum 28 via a line 18 removed and for further thermal treatment by the medium pressure part 14b passed in the heat recovery steam generator 14. This produces a saturated steam 19 which is returned to the drum 28. A portion 22 of this is called the amount of cooling steam passed into the components of the gas turbine group to be cooled, the other The amount of steam 20 undergoes a further heating to superheated in the high-pressure part 14a Steam 21, which is fed directly into the high-pressure combustion chamber 2. This The feed line can also be indirectly via a steam turbine, not shown, preferably a back pressure steam turbine. The removed for cooling purposes Amount of steam 22 from the drum 28 is closed over individual Flow paths 22a / 23a, 22b / 23b, 22c / 23c, 22d, / 23d through the ones to be cooled Components 2, 3, 4, 5 passed, this steam then also into the high-pressure combustion chamber 2 is entered. The removal of saturated steam 22 from the drum 28 can also be from another point in the steam cycle manage where there is a sufficiently high pressure. Such a precaution can be used, for example, wherever the heat recovery steam generator consists of an impression kettle. If handled correctly, this can be done Circuit, including a throttle body integrated in line 21 24, so that the two introduced into the high pressure combustion chamber 2 Amounts of steam 21, 23 have approximately the same quality, which is thereby maximizing the efficiency and specific performance of the system can be achieved.

    BezugszeichenlisteReference list

    11
    Verdichtercompressor
    22nd
    Erste Brennkammer, Hochdruck-BrennkammerFirst combustion chamber, high pressure combustion chamber
    33rd
    Erste TurbineFirst turbine
    44th
    Zweite BrennkammerSecond combustion chamber
    55
    Zweite TurbineSecond turbine
    66
    AnsaugluftIntake air
    77
    Verdichtete LuftCompressed air
    88th
    HeissgaseHot gases
    99
    Teilentspannte HeissgasePartly relaxed hot gases
    1010th
    HeissgaseHot gases
    1111
    AbgaseExhaust gases
    1212th
    Brennstofffuel
    1313
    Brennstofffuel
    1414
    AbhitzedampferzeugerHeat recovery steam generator
    14a14a
    UeberhitzerSuperheater
    14b14b
    VerdampferEvaporator
    14c14c
    EconomizerEconomizer
    1515
    FörderpumpeFeed pump
    1616
    FörderwasserProduction water
    1717th
    Heisswasser Hot water
    1818th
    Heisswasser zum VerdampferHot water to the evaporator
    1919th
    SattdampfSaturated steam
    2020th
    Sattdampf zum UeberhitzerSaturated steam to the superheater
    2121
    Ueberhitzter DampfSuperheated steam
    2222
    SattdampfSaturated steam
    22a22a
    Kühldampfteilmenge für zweite TurbineCooling steam subset for the second turbine
    22b22b
    Kühldampfteilmenge für zweite BrennkammerCooling steam subset for the second combustion chamber
    22c22c
    Kühldampfteilmenge für erste TurbineCooling steam subset for the first turbine
    22d22d
    Kühldampfteilmenge für erste BrennkammerCooling steam partial quantity for the first combustion chamber
    2323
    Ueberhitzter DampfSuperheated steam
    23a23a
    Rücklauf Dampfteilmenge aus zweiter TurbineReturn steam partial quantity from the second turbine
    23b23b
    Rücklauf Dampfteilmenge aus zweiter BrennkammerReturn steam partial quantity from the second combustion chamber
    23c23c
    Rücklauf Dampfteilmenge aus erster TurbineReturn steam partial quantity from the first turbine
    23d23d
    Rücklauf Dampfteilmenge aus erster BrennkammerReturn steam partial quantity from the first combustion chamber
    2424th
    RegelorganGoverning body
    2525th
    RauchgaseFlue gases
    2626
    Wellewave
    2727
    Generatorgenerator
    2828
    Trommeldrum

    Claims (4)

    Verfahren zum Betrieb einer Kraftwerksanlage, im wesentlichen bestehend aus einer Gasturbogruppe und einem der Gasturbogruppe nachgeschalteten Abhitzedampferzeuger, in welchem mindestens eine Dampfmenge erzeugt wird, dadurch gekennzeichnet, dass eine erste unmittelbar aus dem Abhitzedampferzeuger (14) stammenden Menge eines überhitzten Dampfes (21) in eine zur Gasturbogruppe gehörende Brennkammer (2) geleitet wird, dass eine zweite mittelbar oder unmittelbar aus dem Abhitzedampferzeuger (14) stammende Menge eines Sattdampfes (22) über geschlossene Strömungspfade (22a/23a, 22b/23b, 22c/23c, 22d/23d) durch die einzelnen zu kühlenden Komponenten (2, 3, 4, 5) der Gasturbogruppe geleitet wird, und dass diese Dampfmenge (23) anschliessend in die Brennkammer (2) einströmt.Process for operating a power plant, essentially consisting from a gas turbine group and one downstream of the gas turbine group Heat recovery steam generator, in which generates at least one amount of steam is characterized in that a first directly from the Heat recovery steam generator (14) derived amount of superheated steam (21) passed into a combustion chamber (2) belonging to the gas turbine group is that a second directly or indirectly from the heat recovery steam generator (14) originating amount of saturated steam (22) over closed Flow paths (22a / 23a, 22b / 23b, 22c / 23c, 22d / 23d) through the individual to be cooled components (2, 3, 4, 5) of the gas turbine group and that this amount of steam (23) then into the combustion chamber (2) flows in. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die Brennkammer (2) als Hochdruck-Brennkammer einer mit einer sequentieller Verbrennung betriebenen Gasturbogruppe operiert.A method according to claim 1, characterized in that the combustion chamber (2) as a high pressure combustor with sequential combustion operated gas turbine group. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass der Sattdampf (22) durch die erfolgte Kühlung der Komponenten zu überhitztem Dampf (23) wird.A method according to claim 1, characterized in that the saturated steam (22) by cooling the components to superheated steam (23) will. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die zu kühlenden Komponenten (2, 3, 4, 5) mit einer individuelle Sattdampfmenge gekühlt werden.A method according to claim 1, characterized in that the to be cooled Components (2, 3, 4, 5) cooled with an individual amount of saturated steam become.
    EP19970810594 1997-08-25 1997-08-25 Gas turbine with heat recovery generator of superheated steam for injecting into the combustion chamber and of saturated steam of cooling then injecting into the combustion chamber Expired - Lifetime EP0899438B1 (en)

    Priority Applications (2)

    Application Number Priority Date Filing Date Title
    EP19970810594 EP0899438B1 (en) 1997-08-25 1997-08-25 Gas turbine with heat recovery generator of superheated steam for injecting into the combustion chamber and of saturated steam of cooling then injecting into the combustion chamber
    DE59707371T DE59707371D1 (en) 1997-08-25 1997-08-25 Gas turbine with heat recovery generator of superheated steam for injection into the combustion chamber and saturated steam for cooling and then injection into the combustion chamber

    Applications Claiming Priority (1)

    Application Number Priority Date Filing Date Title
    EP19970810594 EP0899438B1 (en) 1997-08-25 1997-08-25 Gas turbine with heat recovery generator of superheated steam for injecting into the combustion chamber and of saturated steam of cooling then injecting into the combustion chamber

    Publications (2)

    Publication Number Publication Date
    EP0899438A1 true EP0899438A1 (en) 1999-03-03
    EP0899438B1 EP0899438B1 (en) 2002-05-29

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    DE (1) DE59707371D1 (en)

    Cited By (5)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US7353654B2 (en) * 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbines using wet compression
    US7353655B2 (en) * 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbine using wet compression
    US7520137B2 (en) 2002-12-02 2009-04-21 Alstom Technology Ltd Method of controlling the injection of liquid into an inflow duct of a prime mover or driven machine
    EP2299178A1 (en) 2009-09-17 2011-03-23 Alstom Technology Ltd A method and gas turbine combustion system for safely mixing H2-rich fuels with air
    US9523311B2 (en) 2007-05-08 2016-12-20 General Electric Technology Gmbh Method of operating a gas turbine, and gas turbine with water injection

    Citations (5)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR343772A (en) * 1903-06-12 1904-10-14 Sebastian Ziani De Ferranti Improvements to elastic fluid turbines
    DE3331153A1 (en) * 1983-08-30 1985-03-14 Brown, Boveri & Cie Ag, 6800 Mannheim Gas turbine system for open process
    GB2158158A (en) * 1984-04-27 1985-11-06 Gen Electric Fluid injection gas turbine engine and method for operating
    DE4409567A1 (en) 1994-03-21 1995-09-28 Abb Management Ag Process for cooling thermally loaded components of a gas turbine group
    EP0731255A1 (en) * 1995-03-07 1996-09-11 ABB Management AG Powerplant system

    Patent Citations (5)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    FR343772A (en) * 1903-06-12 1904-10-14 Sebastian Ziani De Ferranti Improvements to elastic fluid turbines
    DE3331153A1 (en) * 1983-08-30 1985-03-14 Brown, Boveri & Cie Ag, 6800 Mannheim Gas turbine system for open process
    GB2158158A (en) * 1984-04-27 1985-11-06 Gen Electric Fluid injection gas turbine engine and method for operating
    DE4409567A1 (en) 1994-03-21 1995-09-28 Abb Management Ag Process for cooling thermally loaded components of a gas turbine group
    EP0731255A1 (en) * 1995-03-07 1996-09-11 ABB Management AG Powerplant system

    Cited By (8)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    US7353654B2 (en) * 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbines using wet compression
    US7353655B2 (en) * 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbine using wet compression
    US7784286B2 (en) 2001-12-06 2010-08-31 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbines using wet compression
    US7520137B2 (en) 2002-12-02 2009-04-21 Alstom Technology Ltd Method of controlling the injection of liquid into an inflow duct of a prime mover or driven machine
    US9523311B2 (en) 2007-05-08 2016-12-20 General Electric Technology Gmbh Method of operating a gas turbine, and gas turbine with water injection
    EP2299178A1 (en) 2009-09-17 2011-03-23 Alstom Technology Ltd A method and gas turbine combustion system for safely mixing H2-rich fuels with air
    WO2011032839A1 (en) 2009-09-17 2011-03-24 Alstom Technology Ltd A method and gas turbine combustion system for safely mixing h2-rich fuels with air
    US10208958B2 (en) 2009-09-17 2019-02-19 Ansaldo Energia Switzerland AG Method and gas turbine combustion system for safely mixing H2-rich fuels with air

    Also Published As

    Publication number Publication date
    EP0899438B1 (en) 2002-05-29
    DE59707371D1 (en) 2002-07-04

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